摘要
为降低单兵制导火箭弹的成本,同时确保其具有较远的作用距离和较高的命中精度,针对移动目标,进行单兵火箭弹简易制导控制律设计。将飞行弹道进行分段设计,分为筒内运动段、惯性飞行段和导引飞行段。在发射前通过弹载系统和测距仪对目标移动速度进行估计,采用比例导引法实现对目标的跟踪。接下来对STT控制器进行设计,基于典型设计点处控制器参数插值得到不同飞行速度下的控制器参数,确保火箭弹在整个飞行过程中具有较高的控制精度。通过仿真分析可知,所设计的制导控制系统具有较高的鲁棒性。
To reduce the cost of guided individual rocket projectile and ensure that it has a longer striking distance and higher accuracy at the same time, the simple guidance control law of the individual rocket projectile is designed for moving target. The flight trajectory is segmented,including barrel movement segment,inertial flight segment and guiding flight segment. Before launching the speed of the target is estimated by the onboard system and rangefinder,to achieve the goal of tracking by the proportional guidance method. Then the STT controller is designed to ensure the rocket has higher control accuracy based on the controller gains of the typical design points, and the controller gains under different speed are obtained using the interpolation method. Through he simulation analysis, the result shows that the designed guidance control system has high robustness.
出处
《计算机技术与发展》
2016年第11期121-124,129,共5页
Computer Technology and Development
基金
国家自然基金联合基金(U1430113)
中国工程物理研究院科学技术发展基金(2014B0101009)
关键词
火箭弹
简易制导
比例导引
STT
rocket projectile
simple guidance
proportional guidance
STT
